Attitude Sensitive Technology Of Magnetic Gyro Portfolio

According to the need of the Trajectory Correcting ammunition, the attitude measurement technology which based on the magnetic gyro portfolio has been studied in this dissertation, in order to determine the flight body's posture, provide attitude and orientation for the control system.Attitude sensors were used to measure the attitude information relative to a reference bearing. In the actual attitude control system, in order to ensure that the profile of high-precision and high reliability requirements, it is normally required a variety of multi-sensor to compose attitude measurement system and fully display the advantage of a variety of sensors, mutual checking, mutual complement and mutual backup.First, the research purpose and significance are introduced in this dissertation, the current situation and development direction of the attitude sensors at home and abroad are discribed, such as gyroscopes and magneto-resistive sensors, especially the micro-machined gyroscope; and then, the advantages and disadvantages of several attitude measurement methods nowadays are analysised; at last, an attitude measurement program is proposed which based on magnetic detection and micro-gyroscope technology.A low-cost gesture detection system has been proposed in the dissertation which employing three-dimensional magnetic sensors and micro-machined gyroscope; the attitude measurement program is established through the discussion of magnetic sensor attitude measurement theory; several commonly used profile description methods are analysised and the mathematical model,the flight attitude data generation algorithm and solver posture algorithms for this basic posture detection system are built up; and then the flight path data generation system and strapdown inertial navigation simulation system are developed under the MATLAB environment. This simulation system integrated inertial component and posture detection system simulation. Experimental results showed that the simulation system is stable and reliable, the final simulation results achieved the desired effect and the attitude angle error was controlled within 0.001°.Finally, the research work is summarized and the problems of systems are to be analysised in the dissertation; the research direction and development trends of the next step work are to be prospected.